火箭推进2018，Vol.44Issue(3)：30-36,7.
火箭发动机部分进气涡轮设计与流动分析
Design and flow analysis of partial admission turbine for rocket engine
摘要
Abstract
According to the overall performance and structure requirements of a liquid rocket engine, a partial admission, conical nozzle and single-stage supersonic impulse turbine were designed with one-di-mensional engineering method. By solving Reynolds-averaged Navier-Stocks ( RANS ) equations, the three-dimensional viscous steady-state simulation and analysis are performed for the internal flow field of the turbine. For the rotor cascade channel, the influence of area varieties on turbine performance is studied. The results show that the internal streamline of the partial admission turbine is irregular, and there are more eddy flows, complicated rotor cascade shock and serious separation in the blade channel. The total pressure loss in the nozzle channel and rotor cascade channel is more than 20% , and the pressure loss in the later is greater. The variation of rotor cascade channel area has little effect on the overall performance of turbine, but the convergent-divergent type channel can reduce the flow velocity and relieve the gas flow separation, which is helpful in reducing the temperature difference stress of blade.关键词
部分进气涡轮/超声速冲击式涡轮/涡轮设计/流动分析Key words
partial admission turbine/supersonic impulse turbine/turbine design/flow analysis分类
航空航天引用本文复制引用
毛凯,王晓锋,李昌奂,袁伟为..火箭发动机部分进气涡轮设计与流动分析[J].火箭推进,2018,44(3):30-36,7.基金项目
国家重大基础研究项目(613321) （613321）
